NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 200,000 Max Cl/Cd: 55.56 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632a015-il-200000-n5.txt Download as CSV file: xf-naca632a015-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5278 0.08846 0.08457 -0.0436 1.0000 0.0154
-11.750 -0.5600 0.07838 0.07440 -0.0501 1.0000 0.0153
-11.500 -0.5894 0.07126 0.06716 -0.0538 1.0000 0.0151
-11.250 -0.6167 0.06562 0.06139 -0.0554 1.0000 0.0148
-11.000 -0.6418 0.06102 0.05665 -0.0554 1.0000 0.0147
-10.750 -0.6666 0.05694 0.05239 -0.0538 1.0000 0.0147
-10.500 -0.6880 0.05365 0.04894 -0.0509 1.0000 0.0148
-10.250 -0.7086 0.05066 0.04578 -0.0466 1.0000 0.0146
-10.000 -0.7274 0.04812 0.04307 -0.0413 1.0000 0.0148
-9.750 -0.7418 0.04488 0.03960 -0.0366 1.0000 0.0147
-9.500 -0.7506 0.04211 0.03658 -0.0321 1.0000 0.0151
-9.250 -0.7615 0.03839 0.03248 -0.0270 1.0000 0.0158
-9.000 -0.7647 0.03410 0.02761 -0.0230 0.9986 0.0162
-8.750 -0.7387 0.03194 0.02523 -0.0241 0.9897 0.0166
-8.500 -0.7105 0.03030 0.02341 -0.0253 0.9809 0.0170
-8.250 -0.6815 0.02851 0.02141 -0.0264 0.9717 0.0175
-8.000 -0.6511 0.02663 0.01930 -0.0275 0.9621 0.0181
-7.750 -0.6166 0.02468 0.01708 -0.0292 0.9547 0.0190
-7.500 -0.5829 0.02318 0.01541 -0.0307 0.9448 0.0199
-7.250 -0.5490 0.02242 0.01461 -0.0325 0.9336 0.0208
-7.000 -0.5133 0.02144 0.01352 -0.0345 0.9234 0.0224
-6.750 -0.4797 0.02051 0.01249 -0.0361 0.9111 0.0241
-6.500 -0.4488 0.01972 0.01165 -0.0371 0.8974 0.0255
-6.250 -0.4208 0.01886 0.01064 -0.0374 0.8832 0.0275
-6.000 -0.3955 0.01828 0.01006 -0.0373 0.8689 0.0296
-5.750 -0.3716 0.01775 0.00941 -0.0367 0.8554 0.0324
-5.500 -0.3507 0.01723 0.00887 -0.0356 0.8420 0.0348
-5.250 -0.3306 0.01677 0.00831 -0.0342 0.8294 0.0378
-5.000 -0.3109 0.01632 0.00782 -0.0328 0.8180 0.0408
-4.750 -0.2895 0.01600 0.00741 -0.0316 0.8077 0.0447
-4.500 -0.2704 0.01560 0.00698 -0.0301 0.7971 0.0483
-4.250 -0.2485 0.01534 0.00663 -0.0290 0.7882 0.0530
-4.000 -0.2287 0.01497 0.00625 -0.0276 0.7785 0.0579
-3.750 -0.2070 0.01470 0.00587 -0.0264 0.7702 0.0622
-3.500 -0.1860 0.01438 0.00551 -0.0252 0.7611 0.0673
-3.250 -0.1633 0.01415 0.00519 -0.0241 0.7533 0.0747
-3.000 -0.1416 0.01385 0.00490 -0.0230 0.7446 0.0878
-2.750 -0.1251 0.01316 0.00447 -0.0211 0.7373 0.1629
-2.500 -0.1284 0.01145 0.00409 -0.0158 0.7288 0.4850
-2.250 -0.1087 0.01122 0.00405 -0.0140 0.7220 0.5539
-2.000 -0.0863 0.01112 0.00405 -0.0127 0.7138 0.5903
-1.750 -0.0623 0.01108 0.00402 -0.0117 0.7066 0.6185
-1.500 -0.0384 0.01106 0.00405 -0.0107 0.6993 0.6442
-1.250 -0.0146 0.01108 0.00408 -0.0096 0.6919 0.6705
-1.000 0.0095 0.01111 0.00414 -0.0086 0.6850 0.6940
-0.750 0.0349 0.01111 0.00414 -0.0079 0.6773 0.7082
-0.500 0.0613 0.01113 0.00406 -0.0075 0.6709 0.7167
-0.250 0.0877 0.01111 0.00405 -0.0072 0.6628 0.7236
0.000 0.1141 0.01113 0.00399 -0.0068 0.6554 0.7316
0.250 0.1399 0.01111 0.00396 -0.0063 0.6440 0.7387
0.500 0.1652 0.01111 0.00389 -0.0056 0.6305 0.7465
0.750 0.1906 0.01111 0.00383 -0.0050 0.6175 0.7544
1.000 0.2165 0.01113 0.00382 -0.0045 0.6066 0.7622
1.250 0.2422 0.01115 0.00383 -0.0040 0.5972 0.7704
1.500 0.2685 0.01118 0.00384 -0.0036 0.5882 0.7781
1.750 0.2940 0.01120 0.00387 -0.0031 0.5781 0.7872
2.000 0.3203 0.01124 0.00391 -0.0027 0.5686 0.7953
2.250 0.3457 0.01128 0.00394 -0.0022 0.5581 0.8046
2.500 0.3721 0.01133 0.00402 -0.0019 0.5479 0.8133
2.750 0.3976 0.01139 0.00407 -0.0013 0.5372 0.8231
3.000 0.4236 0.01146 0.00415 -0.0009 0.5250 0.8330
3.250 0.4498 0.01154 0.00425 -0.0006 0.5127 0.8432
3.500 0.4757 0.01164 0.00435 -0.0002 0.5004 0.8544
3.750 0.5033 0.01176 0.00448 -0.0001 0.4866 0.8649
4.000 0.5304 0.01189 0.00462 0.0000 0.4705 0.8763
4.250 0.5582 0.01205 0.00477 -0.0001 0.4522 0.8881
4.500 0.5881 0.01225 0.00495 -0.0006 0.4314 0.8987
4.750 0.6168 0.01250 0.00515 -0.0010 0.4095 0.9102
5.000 0.6466 0.01279 0.00538 -0.0017 0.3834 0.9212
5.250 0.6773 0.01316 0.00564 -0.0026 0.3555 0.9307
5.500 0.7061 0.01357 0.00596 -0.0033 0.3312 0.9416
5.750 0.7380 0.01400 0.00631 -0.0046 0.3099 0.9502
6.000 0.7683 0.01446 0.00669 -0.0057 0.2895 0.9595
6.250 0.7984 0.01491 0.00708 -0.0067 0.2730 0.9689
6.500 0.8306 0.01536 0.00749 -0.0082 0.2595 0.9765
6.750 0.8615 0.01581 0.00791 -0.0095 0.2475 0.9852
7.000 0.8940 0.01628 0.00835 -0.0111 0.2359 0.9931
7.250 0.9290 0.01672 0.00880 -0.0133 0.2249 1.0000
7.500 0.9383 0.01708 0.00912 -0.0102 0.2182 1.0000
7.750 0.9507 0.01737 0.00944 -0.0077 0.2105 1.0000
8.250 0.9743 0.01808 0.01016 -0.0024 0.1969 1.0000
8.500 0.9855 0.01849 0.01056 0.0003 0.1906 1.0000
8.750 0.9976 0.01887 0.01097 0.0028 0.1850 1.0000
9.000 1.0079 0.01923 0.01137 0.0057 0.1791 1.0000
9.250 1.0152 0.01969 0.01181 0.0089 0.1738 1.0000
9.500 1.0271 0.02008 0.01228 0.0114 0.1676 1.0000
9.750 1.0367 0.02058 0.01279 0.0140 0.1611 1.0000
10.000 1.0478 0.02109 0.01335 0.0163 0.1536 1.0000
10.250 1.0566 0.02173 0.01398 0.0187 0.1454 1.0000
10.500 1.0681 0.02234 0.01464 0.0206 0.1360 1.0000
10.750 1.0776 0.02309 0.01540 0.0226 0.1273 1.0000
11.000 1.0856 0.02398 0.01626 0.0246 0.1183 1.0000
11.250 1.0948 0.02487 0.01718 0.0263 0.1095 1.0000
11.500 1.1026 0.02591 0.01823 0.0279 0.1020 1.0000
11.750 1.1087 0.02713 0.01945 0.0296 0.0951 1.0000
12.000 1.1162 0.02832 0.02069 0.0309 0.0886 1.0000
12.250 1.1205 0.02980 0.02216 0.0323 0.0833 1.0000
12.500 1.1283 0.03109 0.02354 0.0334 0.0784 1.0000
12.750 1.1324 0.03271 0.02519 0.0344 0.0740 1.0000
13.000 1.1377 0.03431 0.02687 0.0353 0.0703 1.0000
13.250 1.1425 0.03600 0.02863 0.0361 0.0669 1.0000
13.500 1.1444 0.03800 0.03067 0.0368 0.0641 1.0000
13.750 1.1475 0.03995 0.03270 0.0373 0.0615 1.0000
14.000 1.1504 0.04199 0.03484 0.0377 0.0590 1.0000
14.250 1.1512 0.04430 0.03720 0.0380 0.0567 1.0000
14.500 1.1489 0.04698 0.03993 0.0380 0.0549 1.0000
14.750 1.1501 0.04940 0.04247 0.0380 0.0531 1.0000
15.000 1.1502 0.05203 0.04521 0.0379 0.0513 1.0000
15.250 1.1486 0.05492 0.04819 0.0375 0.0497 1.0000
15.500 1.1455 0.05808 0.05143 0.0369 0.0485 1.0000
15.750 1.1402 0.06162 0.05502 0.0361 0.0473 1.0000
16.000 1.1369 0.06497 0.05846 0.0354 0.0462 1.0000
16.250 1.1346 0.06831 0.06194 0.0345 0.0451 1.0000
16.500 1.1315 0.07185 0.06559 0.0335 0.0440 1.0000
16.750 1.1276 0.07558 0.06943 0.0323 0.0430 1.0000
17.000 1.1225 0.07952 0.07346 0.0309 0.0421 1.0000
17.250 1.1171 0.08358 0.07759 0.0294 0.0412 1.0000
17.500 1.1124 0.08753 0.08160 0.0280 0.0405 1.0000
17.750 1.1087 0.09139 0.08551 0.0266 0.0398 1.0000
18.000 1.1034 0.09572 0.09000 0.0247 0.0389 1.0000
18.250 1.0980 0.10011 0.09453 0.0229 0.0381 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63(2)A-015 (naca632a015-il)